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79-21-06: 79-21-06 GENERAL DYNAMICS: Amendment 39-3590 as amended by Amendment 39-3666. Applies to Model 240 series airplanes including those modified for turbo propeller power, certificated in all categories. Compliance required as indicated, unless already accomplished.
To prevent failure of the elevator flight tab spring tube, accomplish the following:
(a) Within 25 hours' time in service after the effective date of this AD, inspect the elevator flight tab spring tube per procedures set forth in Section 2, Accomplishment Instructions, of General Dynamics Service Bulletin 600 (240D) 27-5, dated July 18, 1979.
(b) For elevator flight tab spring tube P/N 240-3540305-24 or P/N 240-3540305-30 with 5,000 hours or more time in service after October 25, 1979, repeat the inspection of paragraph (a) of this AD within 50 hours' time in service from the inspection of paragraph (a) of this AD, and thereafter, at intervals not to exceed 50 hours' time in service from the previous inspection.
(c) For elevator flight tab spring tube P/N 240-3540305-35 or P/N 2D3540305-7 with 10,000 hours or more time in service after October 25, 1979, repeat the inspection of paragraph (a) of this AD within 100 hours' time in service from the inspection of paragraph (a) of this AD, and thereafter, at intervals not to exceed 100 hours' time in service from the previous inspection.
(d) Replace any cracked elevator flight tab spring tube with like serviceable part and revert to the repetitive inspection intervals per paragraph (b) or (c) of this AD, as appropriate.
(e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections required by this AD.
(f) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA, Western Region.
Amendment 39-3590 became effective October 25, 1979.
This Amendment 39-3666 becomes effective January 21, 1980.
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79-18-02: 79-18-02 BOEING: Amendment 39-3537 as amended by Amendment 39-3744. Applies to all Boeing Model 747 airplanes which are equipped with slide/raft assemblies. Compliance is required as indicated. Accomplish the following: \n\tA.\tWithin the next 90 days from the effective date of this AD, unless accomplished within the last 180 days, inspect the firing and packboard lanyards for corrosion in accordance with Boeing Alert Service Bulletin 747-25A2467 and B.F. Goodrich Alert Service Bulletin 25- 051. \n\tB.\tLanyards showing signs of corrosion are to be replaced with new parts in accordance with B.F. Goodrich Alert Service Bulletin 25-051. \n\tC.\tRepeat inspections, described in paragraph A, at intervals not to exceed one (1) year from the date of the last inspection unless the lanyards are replaced as described in Boeing Service Bulletin 747-25A2467, Revision 2, paragraph III E, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. This replacement is terminating action for this Airworthiness Directive. \n\tD.\tUpon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Northwest Region may adjust the inspection interval if the request contains substantiating data to justify the increase for that operator. \n\tThe manufacturer's specifications and procedures identified and described in this directive are incorproated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\tAll persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tAmendment 39-3537 became effective September 4, 1979. \n\tThis amendment 39-3744 becomes effective April 22, 1980.
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2020-05-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A11 airplanes. This AD was prompted by reports that, under certain combinations of airplane configuration and flight conditions, higher than anticipated temperatures could lead to an engine fire warning nuisance message. This AD requires installation of Integrated Air Systems Controller (IASC) software version 5.0. The FAA is issuing this AD to address the unsafe condition on these products.
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79-21-01 R1: 79-21-01 R1 DETROIT DIESEL ALLISON: Amendment 39-3585 as amended by Amendment 39-4123. Applies to 250-B17, 250-B17B, 250-B17C, 250-C20, 250-C20B, and 250-C20C (MIL. T63-A-720) engines equipped with third stage turbine wheel Part Numbers 6898551, 6898567, 6898733, 6898743, 6898753, 6898763, 6899406, 6899415, 6899416, 6899417, 6899418, 6899419, 6896863, 6898823 and 6899364 installed in aircraft certificated in all categories.
Compliance required as follows unless previously accomplished.
(a) For engines that have previously experienced a hot start beyond the established limits, compliance must be accomplished prior to further flight.
(b) For engines that experience a hot start beyond the established limits after the effective date of this AD, compliance must be accomplished prior to further flight, except that the aircraft may be flown in accordance with FAR 21.197 to a base where the removal can be performed.
To preclude possible engine power loss resulting from third stage turbine wheel blade separation, remove the turbine wheels from service if the following temperature-time limits are exceeded and install an FAA Approved part number turbine wheel.
Temperature Range Time Limit
810 degrees - 927 degrees C. 10 seconds maximum
(1490 degrees - 1700 degrees F.)
Over 927 degrees C. 0 seconds
(1700 degrees F.)
The turbine wheels may not be reworked and reinstalled after a hot start.
NOTE: Time at temperature limits is not additive and may be repeated without restriction.
(Detroit Diesel Allison Commercial Service Letter 1051, Rev. 3, for the 250-B17 series engines and Commercial Service Letter 1084, Rev. 3, for the 250-C20 series engines also pertain to this subject.)
Amendment 39-3585 became effective October 16, 1979.
This amendment 39-4123 becomes effective June 3, 1981.
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2020-03-23: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by a report that a fouling condition was found between the generator power cables and the support brackets of the auxiliary-aft fuel tank during production. This AD requires a visual inspection of the generator power cables for damage, installation of protective conduits and edging grommets, and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
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60-04-02: 60-04-02\tBOEING: Amdt. 104 Part 507 Federal Register February 20, 1960. Applies to all Model 707 series aircraft. \n\tDue to recent failures of the wing foreflaps, the following shall be accomplished: \n\t(a)\tAt intervals not to exceed 65 hours' time in service, inspect all foreflaps except the two outboard foreflap sections (P/N's 65-7360-3007 through 65-7360-3010, 65-7360-3023, and 65-7360-3024) on the outboard flaps as follows: \n\t\t(1)\tConduct detail visual inspection of foreflaps for any evidence of cracking. \n\t\t(2)\tBy use of borescope or equivalent, inspect interior web, flanges and cutouts on both inboard and outboard end ribs for cracks or other damage. \n\t(b)\tAny foreflap showing evidence of cracking or other damage must be replaced or repaired in accordance with FAA approved manufacturer's instructions prior to next flight. \n\t(c)\tThe special inspections in (a) above may be discontinued when an inertia damper P/N's 69-11124-1 (left wing) and 69-11124-2 (right wing) has been installed on the foreflaps. \n\t(Boeing Service Bulletin No. 546 (R-2) dated November 18, 1959, covers criteria on the same subject.)
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2020-01-18: The FAA is superseding Airworthiness Directive (AD) 2006-11- 11, which applied to all The Boeing Company Model 757 airplanes. AD 2006-11-11 required incorporating a new revision to the Airworthiness Limitations section of the Instructions for Continued Airworthiness to mandate certain repetitive inspections for fatigue cracking of principal structural elements (PSEs). This AD retains those actions and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
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2020-03-21: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports that main landing gear (MLG) trailing arm assemblies were found with compromised paint finish and corrosion on the axle bore inner diameters due to improper removal of contaminants during manufacturing. This AD requires a one-time inspection to determine if an affected MLG trailing arm assembly is installed, repetitive detailed inspections of the inner diameter of the affected MLG trailing arm assembly axle bore for surface finish discrepancies, corrective actions if necessary, and eventual replacement of primer and paint and application of corrosion preventive compound on the inner diameter of all affected MLG trailing arm assembly axle bores, which terminates the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
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80-18-11: 80-18-11 FAIRCHILD: Amendment 39-3904. Applies to all Model F27 and FH227 series airplanes certificated in all categories.
Compliance required as indicated:
To detect cracks in the front spar web, the upper and lower spar caps, skins, stringers and rib caps on the upper and lower surface of the left and right horizontal stabilizer, accomplish the following:
(a) For F27A, F27F and F27G airplanes, within the next 50 hours in service after the effective date of this AD, unless accomplished within the last 250 hours in service, and at intervals not to exceed 300 hours in service from the last inspection, inspect the horizontal stabilizer for cracks in accordance with Fairchild Service Bulletin F27-55-6, Revision No. 1, dated March 24, 1980, or an approved equivalent. The 300 hour repetitive inspection may be increased to 1200 hours in service after incorporation of Fairchild Service Bulletin F27-55-7, dated July 20, 1965, or an approved equivalent.
(b) For F27J and F27M airplanes, within the next 50 hours in service after the effective date of this AD, unless accomplished within the last 10 hours in service, and at intervals not to exceed 60 hours in service from the last inspection, inspect the horizontal stabilizer for cracks in accordance with the above Service Bulletin or an approved equivalent. The 60 hour repetitive inspection may be increased to 150 hours in service after incorporation of Fairchild Service Bulletin F27-55-7, dated July 20, 1965, or an approved equivalent. It may be increased to 350 hours in service after incorporation of Fairchild Service Bulletins F27-55-11, dated November 5, 1979, and F27-55-12, dated December 6, 1966, or an approved equivalent.
(c) For FH227 type airplanes and for F27A, F27G, F27J, F27F, and F27M airplanes having the FH227 horizontal stabilizer installed, comply with Paragraph (d) within the next 150 hours in service after the effective date of this AD, unless accomplished within the last1050 hours in service, and at intervals not to exceed 1200 hours in service from the last inspection.
(d) Inspect the horizontal stabilizer for cracks in accordance with the accomplishment instructions (except Note 1) of Fairchild Service Bulletin FH227-55-13, Revision No. 1, dated March 24, 1980, or an approved equivalent, using X-Ray or dye penetrant in conjunction with a glass of at least 10-power or an approved equivalent.
(e) Repair cracked parts or replace them, before further flight, with an unused part of the same part number or an approved equivalent, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed.
(f) Equivalent inspections, repairs or parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
(g) Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance times specified in this AD.
This AD supersedes AD's 66-27-05 and 66-28-03.
This amendment is effective September 4, 1980.
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2019-26-10: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701 & 702) airplanes; Model CL-600-2D15 (Regional Jet Series 705) airplanes; Model CL-600-2D24 (Regional Jet Series 900) airplanes; and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a report of incorrectly installed flight compartment door edge protection plates on both sides of the upper decompression panel. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate a functional check of the flight compartment door decompression latches. The FAA is issuing this AD to address the unsafe condition on these products.
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